EP0721061B1 - Temperaturregelungssystem für Schmieröl und Brennstoff in einem Turbostrahltriebwerk - Google Patents

Temperaturregelungssystem für Schmieröl und Brennstoff in einem Turbostrahltriebwerk Download PDF

Info

Publication number
EP0721061B1
EP0721061B1 EP96400015A EP96400015A EP0721061B1 EP 0721061 B1 EP0721061 B1 EP 0721061B1 EP 96400015 A EP96400015 A EP 96400015A EP 96400015 A EP96400015 A EP 96400015A EP 0721061 B1 EP0721061 B1 EP 0721061B1
Authority
EP
European Patent Office
Prior art keywords
oil
fuel
circuit
closed
heat exchanger
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP96400015A
Other languages
English (en)
French (fr)
Other versions
EP0721061A1 (de
Inventor
Bruno Albert Beutin
Françis Georges Albert Garnier
Joel Creti
Michel Georges Hugues
Jean-Pierre Donnadieu
Jean-Loic Hervé Lecordix
Claude Paul Henri Maignan
Gilles Claude Gabriel Massot
Christophe Jean François Thorel
Carole Claudine Touron
Gérard Marie René Marcel Vennin
Jean-Marie Noel Pincemin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0721061A1 publication Critical patent/EP0721061A1/de
Application granted granted Critical
Publication of EP0721061B1 publication Critical patent/EP0721061B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to the regulation of the temperatures of aviation engine oil and fuel, by heat transfer between oil and fuel.
  • turbojets have two oil circuits separate: a first closed circuit for traffic and cooling of the lubricating oil of the internal structures of the turbojet engine such as bearings, and a second closed circuit for circulation and cooling of the lubricating oil means alternator drive.
  • the fuel flow which supplies the injection devices of the turbojet engine in operation is delivered by a fuel system that takes fresh fuel in the wings. To facilitate combustion, the fuel is heated in the fuel circuit up to a high limit temperature which must not not be exceeded if you do not want to cause partial vaporization or a decomposition of the fuel which causes a malfunction of pumps and regulation equipment engine.
  • Fuel rates are based on orders given by the pilot.
  • the oil flow in the first closed circuit depends on the rotational speed of the turbojet engine, and the heat conveyed by this oil is a function of the charge of the turbojet engine.
  • the alternator being driven at constant speed
  • the oil flow from the second closed circuit is substantially constant and the heat conveyed by this oil is a function of the electrical demand of the aircraft, and of thermal releases from the integrated mechanical transmissions which connect the alternator to a rotating part of the turbojet engine.
  • These mechanical transmissions dissipate a lot of heat, even when the motors that drive them are idling.
  • Thermal energy dissipated in the second oil circuit represents 5 to 15% of that dissipated in the engine oil circuit, when operating at full power and can reach 50% in idle conditions.
  • the fuel temperature must not be higher than 150 ° C. Due to the excellent performance of the reducer turbojets and high dilution rate, the flow of fuel through the engine is no longer sufficient to dissipate the heat dissipated by the transmissions of alternators and by the engine lubricating oil.
  • US Patent 4,151,710 describes a cooling system oils from a turbojet engine in which the cooling of the lubrication of the alternator drives is achieved by a second air / oil exchanger mounted in series with a heat exchanger oil / fuel heat disposed downstream of a first heat exchanger oil / fuel heat of the first closed circuit in the direction of fuel flow. It is expected that in the descent phases of the aircraft, the fuel overheated as a result of the recirculation of the fuel is cooled by oil from the second closed circuit in the second heat exchanger, which requires the use of a air / oil heat exchanger in the second closed circuit.
  • US Patent 4,741,152 describes a system corresponding to the preamble of claim 1, having two lubrication circuits which each have an air / oil heat exchanger and an exchanger of oil / fuel heat.
  • the oil / fuel heat exchanger cooling system of the lubrication oil of the drives of the alternator is arranged upstream of the other heat exchanger oil / fuel on the fuel system.
  • US Patent 5,121,598 shows a cooling device lubricating oil from the alternator drives which has an oil / fuel heat exchanger on a return of fuel to the wing tanks.
  • the purpose of the present invention is to provide a system of temperature regulation in a turbojet engine of the type mentioned above which overcomes the disadvantages mentioned above and which allows in particular to facilitate starting in cold weather, to avoid the fuel overheating in the wings when the turbojet is in rotation on the ground in hot weather, and to sufficiently warm the fuel in flight at altitude.
  • Means are also provided for regulating the oil flow. taken from the first closed circuit and passing through each of said heat exchangers, depending on flight conditions and temperatures.
  • the lubricating oil of the means drive of the alternator heats the oil of the first closed circuit in all flight conditions, and in particular when starting at cold.
  • this heat exchanger being of the oil / oil type, there there is no risk of pollution of closed circuits by a natural fluid ⁇ different in the event of a leak in said exchanger.
  • the heat given off by the alternator drive means is not dissipated in the fuel contained in the wing tanks, which removes the disadvantages of overheating fuel in the wings when the aircraft waits too long on the ground for takeoff in the hot countries.
  • the heat available in the engine oil is increased by additional heat from the means alternator drive. In flight, at altitude, the heat available in the engine oil becomes sufficient to heat the fuel cold.
  • the difference between the temperature of the cold fuel and the temperature of the oil circulating in the first closed circuit is increased in all flight conditions, which improves heat exchange and authorizes a smaller oil / fuel exchanger.
  • the drawing shows a turbojet engine 1, a movable part of which rotation causes an alternator 2 at constant speed via a integrated mechanical transmission 3.
  • the heat dissipated in the turbojet engine 1 is conveyed to the exterior by a first closed circuit 4 which comprises in the direction of the oil flow a heat exchanger 5 of the air / oil type in which circulates a cooling air A taken from the cold flow by a controlled shutter 6 a heat exchanger 7 of the type oil / fuel, a heat exchanger 8, of the oil / oil type and a oil pump 9 driven directly by the turbojet engine 1.
  • Lubricating oil for integrated mechanical transmission 3 of the alternator 2 circulates in a second closed circuit 10 which passes by the oil / oil heat exchanger 8 in which the oil circulating in the second circuit 10 is cooled by heating the oil of the first closed circuit 4.
  • the fuel is taken from the tank 11 located in the wing of aircraft by a booster pump 12, then transits, via the fuel 13, through the heat exchanger 7, the high pump pressure 14 and the fuel flow regulator 15.
  • the regulator flow 15 supplies the fuel injectors 16 of the turbojet engine of the amount of fuel required based on orders received from the station and recycles the surplus fuel supplied by the high pressure by a recirculation circuit 17 to the pump booster 12 or the tank 11.
  • a line 18 takes fuel from high pressure in the fuel system 13 between the high pump pressure 14 and the flow regulator 15 to supply the controls 19 engine hydraulics, using fuel, such as cylinders.
  • the first closed circuit 4 further comprises pipes for bypass, respectively 20, 21 and 22, between the input and the output of each of the heat exchangers 5, 7 and 8, in order to regulate the flow of oil passing through them under the action of controlled valves 23, 24 and 25 by a control system based on flight conditions, temperatures of the various fluids and set values.
  • valves 23 and 25 When starting in cold weather, valves 23 and 25 are positioned so that all of the oil flowing through the first closed circuit 4 passes through the bypass line 20 on the one hand and through the oil / oil heat exchanger 8 thus allowing heating the oil supplied to the engine by the oil pump 9, by means of heat taken from the second closed circuit 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Lubrication Of Internal Combustion Engines (AREA)

Claims (2)

  1. Temperatur-Steuersystem für Öl und Treibstoff einer Turbomaschine (1), die mit einem Generator (2) versehen ist, der mechanisch mit konstanter Geschwindigkeit durch ein Drehelement der Turbomaschine angetrieben wird, wobei die Turbomaschine (1) einen ersten geschlossenen Kreislauf (4) zur Zirkulation und zur Kühlung des Schmieröls der Turbomaschine (1), einen zweiten geschlossenen Kreislauf (10) zur Zirkulierung und Kühlung des Schmieröls der Antriebseinrichtungen (3) des Generators sowie einen Treibstoff-Kreislauf (13) aufweist, der zur Zufuhr einer Treibstoffmenge zu der Turbomaschine (1) dient, und mit
    Temperatur-Steuereinrichtungen für den Treibstoff und das Öl in jedem der geschlossenen Kreisläufe, sowie
    einem Öl/Treibstoff-Wärmetauscher (7), der zwischen dem ersten geschlossenen Ölkreislauf (4) und dem Treibstoff-Kreislauf (13) vorgesehen ist und zur Erwärmung des Treibstoffs durch Kühlung des durch den Wärmetauscher (7) hindurchgehenden Öls dient, und
    einen Luft/Öl-Wärmetauscher (5), der in dem ersten geschlossenen Ölkreislauf (4) vorgesehen ist, und stromaufwärts des Öl/Treibstoff-Wärmetauschers (7) in Flußrichtung des Öls in dem ersten geschlossenen Ölkreislauf (4) vorgesehen ist,
       dadurch gekennzeichnet, daß die Temperatur-Steuereinrichtungen aufweisen:
    einen Öl/Öl-Wärmetauscher (8), der zwischen dem ersten geschlossenen Ölkreislauf (4) und dem zweiten geschlossenen Ölkreislauf (10) vorgesehen ist und stromabwärts des Öl/Treibstoff-Wärmetauschers (7) in der Flußrichtung des Öls in dem ersten geschlossenen Ölkreislauf (4) vorgesehen ist, wobei der Öl/Öl-Wärmetauscher (8) zur Kühlung des Öls dient, das in den zweiten geschlossenen Kreislauf (10) strömt, durch Erwärmung des Öls des ersten geschlossenen Kreislaufs (4), das den Öl/Öl-Wärmetauscher (8) durchströmt.
  2. System nach Anspruch 1,
    dadurch gekennzeichnet, daß die Temperatur-Steuereinrichtungen weiterhin Einrichtungen (20, 21, 22, 23, 24, 25) zur Steuerung der Ölmenge aufweisen, die in dem ersten geschlossenen Kreislauf (4) entnommen wird und jeden der Wärmetauscher (5, 7, 8) abhängig von Flug- und Temperaturbedingungen durchströmt.
EP96400015A 1995-01-04 1996-01-04 Temperaturregelungssystem für Schmieröl und Brennstoff in einem Turbostrahltriebwerk Expired - Lifetime EP0721061B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9500031 1995-01-04
FR9500031A FR2728938A1 (fr) 1995-01-04 1995-01-04 Systeme de regulation des temperatures de l'huile et du carburant dans un turboreacteur

Publications (2)

Publication Number Publication Date
EP0721061A1 EP0721061A1 (de) 1996-07-10
EP0721061B1 true EP0721061B1 (de) 1998-04-22

Family

ID=9474852

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96400015A Expired - Lifetime EP0721061B1 (de) 1995-01-04 1996-01-04 Temperaturregelungssystem für Schmieröl und Brennstoff in einem Turbostrahltriebwerk

Country Status (4)

Country Link
US (1) US5615547A (de)
EP (1) EP0721061B1 (de)
DE (1) DE69600246T2 (de)
FR (1) FR2728938A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107905900A (zh) * 2017-10-25 2018-04-13 北京航天宏恩动力技术有限公司 微型涡轮喷气发动机燃油控制方法及装置、存储介质

Families Citing this family (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0318400D0 (en) * 2003-08-06 2003-09-10 Rolls Royce Plc A fluid system
US7204090B2 (en) * 2004-06-17 2007-04-17 Pratt & Whitney Canada Corp. Modulated current gas turbine engine starting system
US7571596B2 (en) * 2005-12-14 2009-08-11 Hamilton Sundstrand Corporation Vacuum system for membrane fuel stabilization unit
US8776952B2 (en) * 2006-05-11 2014-07-15 United Technologies Corporation Thermal management system for turbofan engines
US8205427B2 (en) * 2006-11-09 2012-06-26 United Technologies Corporation Interdependent lubrication systems in a turbine engine
US7908840B2 (en) * 2006-11-29 2011-03-22 United Technologies Corporation Turbine engine with integrated generator having shared lubrication system
EP1933077B1 (de) * 2006-12-12 2010-05-05 Techspace aero Verfahren und System zum Schmieren von Turbomaschinen
FR2915238A1 (fr) * 2007-04-23 2008-10-24 Airbus France Sa Procede et systeme pour le demarrage d'un turbomoteur par temps froid.
RU2353787C1 (ru) * 2007-09-06 2009-04-27 Открытое акционерное общество "Российские железные дороги" (ОАО "РЖД") Газотурбинная установка
US20090078508A1 (en) * 2007-09-20 2009-03-26 Honeywell International, Inc. Electric motor driven lubrication supply system shutdown system and method
US20090313999A1 (en) * 2008-05-13 2009-12-24 Scott Hunter Method and apparatus for controlling fuel in a gas turbine engine
US7984606B2 (en) * 2008-11-03 2011-07-26 Propulsion, Gas Turbine, And Energy Evaluations, Llc Systems and methods for thermal management in a gas turbine powerplant
DE102008057828A1 (de) * 2008-11-18 2010-05-20 Rolls-Royce Deutschland Ltd & Co Kg Fluggasturbinen-Ölsystemerwärmung
US8740102B2 (en) * 2008-12-30 2014-06-03 Rolls-Royce Corporation Gas turbine engine valve
US7997062B2 (en) * 2009-01-29 2011-08-16 Pratt & Whitney Canada Corp. Dual channel regulated fuel-oil heat exchanger
US8438850B2 (en) * 2009-02-17 2013-05-14 General Electric Company Waste heat utilization for pre-heating fuel
GB2478934B (en) * 2010-03-24 2012-06-13 Rolls Royce Plc Fuel heat management system
US9004154B2 (en) * 2010-08-31 2015-04-14 Pratt & Whitney Combination fuel-oil and air-oil heat exchanger
DE102011012863A1 (de) * 2011-03-03 2012-09-06 Rolls-Royce Deutschland Ltd & Co Kg Ölversorgungssystem für ein Flugtriebwerk
US9109464B2 (en) * 2011-08-31 2015-08-18 United Technologies Corporation Distributed lubrication system
FR2979671B1 (fr) * 2011-09-07 2017-02-10 Snecma Circuits d'huile et de carburant dans une turbomachine
US9429072B2 (en) * 2013-05-22 2016-08-30 General Electric Company Return fluid air cooler system for turbine cooling with optional power extraction
US9644898B2 (en) 2013-07-09 2017-05-09 The Boeing Company Systems and methods for heat balance and transport for aircraft hydraulic systems
US9644648B2 (en) * 2013-07-09 2017-05-09 The Boeing Company Systems and methods for heat balance and transport for aircraft hydraulic systems
US20160201563A1 (en) * 2013-09-10 2016-07-14 United Technologies Corporation Fuel management system for a turbine engine
US10082078B2 (en) * 2015-03-25 2018-09-25 United Technologies Corporation Aircraft thermal management system
FR3034464B1 (fr) * 2015-04-03 2017-03-24 Snecma Refroidissement du circuit d'huile d'une turbomachine
US9920779B2 (en) * 2015-08-03 2018-03-20 The Boeing Company Aircraft hydraulic thermal management system
US10612860B2 (en) * 2016-05-23 2020-04-07 Hamilton Sunstrand Corporation Multiple flow heat exchanger
US10544717B2 (en) 2016-09-07 2020-01-28 Pratt & Whitney Canada Corp. Shared oil system arrangement for an engine component and a generator
FR3056641B1 (fr) * 2016-09-23 2020-06-12 Safran Systeme de refroidissement d'un circuit d'un premier fluide d'une turbomachine
EP3336320B1 (de) * 2016-12-14 2020-08-12 Airbus Operations, S.L. Ölheizungssystem für ein turbinentriebwerk zur reduzierung des anfahrmoments
US10876497B2 (en) * 2017-08-18 2020-12-29 Rolls-Royce North American Technologies Inc. Method for fast thermalization and thermal management operation optimization
US11162419B2 (en) * 2018-02-12 2021-11-02 General Electric Company Method and structure for operating engine with bowed rotor condition
FR3096396B1 (fr) * 2019-05-24 2021-04-23 Safran Aircraft Engines système HYDROMECANIQUE DE REGULATION D’HUILE DE LUBRIFICATION D’UNE TURBOMACHINE AVEC REGULATION DU DEBIT D’HUILE
US11492969B2 (en) 2019-12-09 2022-11-08 Meggitt Aerospace Limited Engine thermal management methods and control systems
FR3116858B1 (fr) * 2020-12-01 2022-10-28 Safran Aircraft Engines Ensemble pour turbomachine d’aeronef comprenant une vanne passive de contournement d’un echangeur de chaleur carburant / huile
CN114396341A (zh) * 2022-01-05 2022-04-26 北京航空航天大学 一种组合发动机用中间循环热量排散系统
GB2622211A (en) 2022-09-06 2024-03-13 Rolls Royce Plc A thermal management system for an aircraft
GB2622207A (en) * 2022-09-06 2024-03-13 Rolls Royce Plc A thermal management system for an aircraft
GB2622208A (en) 2022-09-06 2024-03-13 Rolls Royce Plc A thermal management system for an aircraft

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB519752A (en) * 1938-05-27 1940-04-04 Brevets Aero Mecaniques Improvements in and relating to lubricant-cooling means for liquid-cooled internal combustion engines
DE1195088B (de) * 1963-07-25 1965-06-16 Licentia Gmbh Schmieroelkuehleinrichtung einer Gasturbinen-anlage
US4151710A (en) * 1977-03-11 1979-05-01 United Technologies Corporation Lubrication cooling system for aircraft engine accessory
US4474001A (en) * 1981-04-01 1984-10-02 United Technologies Corporation Cooling system for the electrical generator of a turbofan gas turbine engine
US4696156A (en) * 1986-06-03 1987-09-29 United Technologies Corporation Fuel and oil heat management system for a gas turbine engine
US4705100A (en) * 1986-07-11 1987-11-10 Grumman Aerospace Corp. Fuel/auxiliary oil thermal management system
GB8907788D0 (en) * 1989-04-06 1989-05-17 Rolls Royce Plc Management of heat generated by aircraft gas turbine installations
US4969796A (en) * 1989-10-30 1990-11-13 Westinghouse Electric Corp. Method and apparatus for cooling shaft seals
GB9027782D0 (en) * 1990-12-21 1991-02-13 Rolls Royce Plc Heat exchanger apparatus
US5105875A (en) * 1991-01-10 1992-04-21 Sundstrand Corporation Cooling system for auxiliary power unit
GB2260577B (en) * 1991-10-16 1994-10-05 Rolls Royce Plc Gas turbine engine starting

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107905900A (zh) * 2017-10-25 2018-04-13 北京航天宏恩动力技术有限公司 微型涡轮喷气发动机燃油控制方法及装置、存储介质

Also Published As

Publication number Publication date
FR2728938A1 (fr) 1996-07-05
US5615547A (en) 1997-04-01
DE69600246D1 (de) 1998-05-28
FR2728938B1 (de) 1997-02-14
EP0721061A1 (de) 1996-07-10
DE69600246T2 (de) 1998-08-13

Similar Documents

Publication Publication Date Title
EP0721061B1 (de) Temperaturregelungssystem für Schmieröl und Brennstoff in einem Turbostrahltriebwerk
US7984606B2 (en) Systems and methods for thermal management in a gas turbine powerplant
EP1329617B1 (de) Fluidströmungssystem für ein Gasturbinentriebwerk
EP2837798B1 (de) Beheiztes Bypassventil für Wärmetauscher
FR2503256A1 (fr) Equilibrage de flux thermique entre des elements associes a une turbine a gaz
FR2914365A1 (fr) Systeme de refroidissement et de regulation en temperature d'equipements d'un ensemble propulsif d'aeronef.
FR2979671A1 (fr) Circuits d'huile et de carburant dans une turbomachine
FR2478742A1 (fr) Systeme de recuperation d'energie pour turbine a gaz
FR3095092A1 (fr) Dispositif de refroidissement et de lubrification d’un groupe motopropulseur électrique d’un véhicule automobile électrique ou hybride
CA2924105A1 (fr) Turbomachine adaptee a fonctionner en mode vireur
EP3149312B1 (de) Vorrichtung und verfahren zum vorwärmen von brennstoff in einer turbomaschine
FR2536842A1 (fr) Systeme de recuperation de chaleur de l'huile de lubrification d'un moteur et procede de recuperation de cette chaleur
EP3418192B1 (de) System zur rückgewinnung von wärmeenergie eines hauptleistungsübertragungsgetriebes eines luftfahrzeugs zur beheizung der kabine des luftfahrzeugs
FR2720442A1 (fr) Installation d'alimentation en carburant d'un turboréacteur.
WO2015052424A1 (fr) Refroidissement d'un moteur alternatif a combustion interne
FR3099203A1 (fr) Circuit de lubrification d’une turbomachine d’aeronef
US10738749B1 (en) Method of using heat from fuel of common-rail injectors
FR2950572A1 (fr) Systeme et procede de controle de la temperature de l'habitacle d'un vehicule automobile
EP1681456A1 (de) Anlage zur thermischen Regelung des in einen Motor eingelassenen Gases
EP4049934B1 (de) Luftfahrzeug, das einen motor und ein kühlsystem auf wasserstoffbasis umfasst
WO2020201032A1 (fr) Système de refroidissement de turboréacteur pour aéronef
FR3035445A1 (fr) Moteur d'avion

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19960120

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

17Q First examination report despatched

Effective date: 19971016

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19980427

REF Corresponds to:

Ref document number: 69600246

Country of ref document: DE

Date of ref document: 19980528

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20120517 AND 20120523

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20131223

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20131219

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20150121

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 69600246

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20150104

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150104

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150801